DST-100

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Engine Model: DST-100. Designer: Isayev. Propellants: N2O4/UDMH. Thrust(vac): 100 N (20 lbf). Isp: 276 sec. Burn time: 10,000 sec. Mass Engine: 1.10 kg (2.40 lb). Chambers: 1. Chamber Pressure: 15.00 bar. Area Ratio: 43.00. Oxidizer to Fuel Ratio: 1.85. Thrust to Weight Ratio: 9.09. Country: Russia. Status: In Production.

Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions

Engine Model: DST-100A. Designer: Isayev. Propellants: N2O4/UDMH. Thrust(vac): 100 N (20 lbf). Isp: 304 sec. Burn time: 50,000 sec. Mass Engine: 1.50 kg (3.30 lb). Chambers: 1. Chamber Pressure: 7.70 bar. Area Ratio: 100.00. Oxidizer to Fuel Ratio: 1.85. Thrust to Weight Ratio: 6.66. Country: Russia. Status: In Production.

Bi-propellant hypergolic (self-igniting) engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-100. 450,0000 ignitions

Bibliography:

Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1998 via Dietrich Haeseler.

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